CN111579204B - Sensing mechanism of two-dimensional airfoil model - Google Patents
Sensing mechanism of two-dimensional airfoil model Download PDFInfo
- Publication number
- CN111579204B CN111579204B CN202010473766.7A CN202010473766A CN111579204B CN 111579204 B CN111579204 B CN 111579204B CN 202010473766 A CN202010473766 A CN 202010473766A CN 111579204 B CN111579204 B CN 111579204B
- Authority
- CN
- China
- Prior art keywords
- dimensional airfoil
- airfoil model
- sensor group
- hole
- section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 21
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 claims 2
- 238000005259 measurement Methods 0.000 abstract description 5
- 238000002474 experimental method Methods 0.000 description 5
- 230000002441 reversible effect Effects 0.000 description 5
- 238000009530 blood pressure measurement Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 229920000122 acrylonitrile butadiene styrene Polymers 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000007517 polishing process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L15/00—Devices or apparatus for measuring two or more fluid pressure values simultaneously
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L19/00—Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
- G01L19/14—Housings
- G01L19/147—Details about the mounting of the sensor to support or covering means
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention relates to a sensing mechanism of a two-dimensional airfoil model. This sensing mechanism includes: a pressure sensor group, a plurality of first conduits, a second conduit, and a cavity; the pressure sensor group is vertically fixed in a mounting hole on the surface of the two-dimensional airfoil model, and the pressure measuring surface of each pressure sensor in the pressure sensor group is vertical to the surface of the two-dimensional airfoil model; the surface of the two-dimensional airfoil model is provided with a plurality of mounting holes perpendicular to the surface of the two-dimensional airfoil model; the cavity is fixed inside the two-dimensional airfoil model; the reference pressure end of the pressure sensor in the pressure sensor group is connected to the cavity through the first guide pipe, and a plurality of pressure sensors in the pressure sensor group correspond to the first guide pipes one by one; the cavity is connected to a first end of the second conduit, and a second end of the second conduit is disposed in the atmosphere outside the two-dimensional airfoil model. The invention can improve the measurement precision of the two-dimensional airfoil surface pressure distribution.
Description
Technical Field
The invention relates to the field of aerodynamics, in particular to a sensing mechanism of a two-dimensional airfoil model.
Background
The rotor is a key part of the helicopter, can provide lift force, thrust force and moment required by maneuvering flight for the helicopter, and the aerodynamic analysis of the rotor is the core problem of the aerodynamics of the helicopter.
Two-dimensional airfoil surface pressure measurement in wind tunnel is one of the main means of studying rotor aerodynamic problem, however the pressure measuring device that current experimental apparatus adopted mainly utilizes the pitot tube, when using the pitot tube to measure pressure, has following shortcoming:
the pitot tube per se can generate disturbance to a flow field, so that the measurement precision is reduced, and the error is more obvious when the dynamic pressure is measured.
When the pitot tube is used for experiments, theoretically, air in the pitot tube and the rubber tube must be completely exhausted, then the lower end of the pitot tube is placed in water flow, and an inlet of the total pressure tube is opposite to the flow velocity direction of a measuring point. However, in practical application, the bubbles are not easy to be discharged completely, once the lower end of the air bubble is separated from the water surface, the air bubble needs to be discharged again after entering, and the process is complicated. In addition, the direction of the flow velocity at the point of measurement is not easily achieved.
Disclosure of Invention
The invention aims to provide a sensing mechanism of a two-dimensional airfoil model, so as to improve the measurement precision of the surface pressure distribution of a two-dimensional airfoil.
In order to achieve the purpose, the invention provides the following scheme:
a sensing mechanism for a two-dimensional airfoil model, comprising: a pressure sensor group, a plurality of first conduits, a second conduit, and a cavity;
the pressure sensor group is vertically fixed in a mounting hole on the surface of the two-dimensional airfoil model, and the pressure measuring surface of each pressure sensor in the pressure sensor group is vertical to the surface of the two-dimensional airfoil model; the surface of the two-dimensional airfoil model is provided with a plurality of mounting holes perpendicular to the surface of the two-dimensional airfoil model;
the cavity is fixed inside the two-dimensional airfoil model; the reference pressure end of the pressure sensor in the pressure sensor group is connected to the cavity through the first guide pipe, and a plurality of pressure sensors in the pressure sensor group correspond to the first guide pipes one by one; the cavity is connected to a first end of the second conduit, and a second end of the second conduit is disposed in the atmosphere outside the two-dimensional airfoil model.
Optionally, the two-dimensional airfoil model is provided with a plurality of through holes along the span direction, and the rotating shaft of the two-dimensional airfoil model is arranged in the second through hole on the geometric leading edge side of the two-dimensional airfoil model.
Optionally, the two-dimensional airfoil model comprises a first end section, a middle section and a second end section, the first end section, the middle section and the second end section are sequentially fixed by pins, and the first end section, the middle section and the second end section are fixed in a span-wise direction by gluing; the pressure sensor set, the first conduit, and the cavity are all located within the intermediate section.
Optionally, a first groove and a second groove are formed in the middle section;
the cavity is fixed in the first groove, part of the pipe section of the first end of the second pipe is positioned in the first groove, and part of the pipe section of the second end of the second pipe passes through the through hole in the first end section and extends to the outside of the two-dimensional airfoil model;
a plurality of said first conduits being secured within said second recess;
the second groove is communicated with the first groove; and a signal wire of the pressure sensor group sequentially passes through the second groove, the first groove and the through hole in the second end section to extend to the outside of the two-dimensional airfoil model.
Optionally, the pressure sensor group includes a first sensor group and a second sensor group, and the first sensor group and the second sensor group each include a plurality of pressure sensors;
the first sensor group is fixed in a mounting hole in the upper surface of the two-dimensional airfoil model, and the second sensor group is fixed in a mounting hole in the lower surface of the two-dimensional airfoil model; and the pressure sensors of the first sensor group and the pressure sensors of the second sensor group are arranged in a staggered manner in the chord direction of the two-dimensional airfoil model.
Optionally, the number of the pressure sensors of the first sensor group is greater than the number of the pressure sensors of the second sensor group.
Optionally, the first sensor group includes 14 pressure sensors, and the second sensor group includes 8 pressure sensors.
Optionally, the pressure sensors in the pressure sensor group are HTP504 type micro dynamic pressure sensors.
Optionally, the mounting hole on the surface of the two-dimensional airfoil model is a stepped hole, the stepped hole comprises a first hole section and a second hole section, the first hole section is close to the hole section inside the two-dimensional airfoil model, the second hole section is close to the hole section on the surface of the two-dimensional airfoil model, and the diameter of the first hole section is smaller than that of the second hole section.
Optionally, the mounting hole further comprises a gasket, the gasket is located at the second hole end of the second hole section, and the gasket is used for filling the two-dimensional airfoil model surface part which is vacant in the position of the mounting hole; and the second hole end of the second hole section is one end positioned on the surface of the two-dimensional airfoil model, and the first hole end of the second hole section is connected with the first hole section.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the miniature dynamic pressure sensor is arranged in the airfoil model, so that the integrity of the surface of the two-dimensional airfoil model can be kept, the smoothness of the surface of the model is not damaged, the device cannot influence a flow field, the measurement precision is high and can reach 0.03Pa, and the error is less than two thousandths.
In addition, the miniature dynamic pressure sensors arranged on the upper surface and the lower surface of the two-dimensional airfoil model are staggered in a mode of carrying out unfolding movement on the miniature dynamic pressure sensors, the miniature dynamic pressure sensors on the geometric trailing edge of the two-dimensional airfoil model are more tightly arranged in the arrangement mode, the measured dynamic pressure data on the geometric trailing edge is closer to the actual situation, and favorable support is provided for accurately researching the dynamic stall problem of the reverse flow area. And the micro dynamic pressure sensor has short response time and high sampling rate of 3KHz, and can acquire dynamic pressure data of the surface of the two-dimensional airfoil model in real time and reflect unsteady aerodynamic force of the surface of the airfoil in real time. The experiment repeatability is high, and the sensor is once only installed inside the model after, need not to install the sensor again alright carry out many times experiment, improves work efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a schematic view of a sensing mechanism for a reverse view angle of a two-dimensional airfoil model according to the present invention;
FIG. 2 is a schematic view of a mounting position of a surface sensor under a two-dimensional airfoil model according to the present invention;
FIG. 3 is a schematic view of a sensing mechanism for a front view of a two-dimensional airfoil model according to the present invention;
FIG. 4 is a schematic view of the mounting position of a surface sensor on a two-dimensional airfoil model according to the present invention;
FIG. 5 is a schematic view of a two-dimensional airfoil model chord-wise sensor mounting location in accordance with the present invention;
FIG. 6 is a schematic view of the connection of the pressure sensor of the present invention to the cavity;
FIG. 7 is a schematic view of the position of the sensor of the present invention secured to the mounting hole.
Number designation in the figures: the method comprises the following steps of 1-a two-dimensional airfoil model first end section, 2-a two-dimensional airfoil model middle section, 3-a two-dimensional airfoil model second end section, 4-a front cover plate, 5-a cavity, 6-a cavity connecting pipe, 7-a pressure sensor, 8-a first conduit, 9-a second conduit, 10-a signal line, 11-a rotating shaft, 12-a backing plate and 13-a back cover plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
FIG. 1 is a schematic view of a sensing mechanism for a reverse view angle of a two-dimensional airfoil model according to the present invention. As shown in fig. 1, the sensing mechanism of the two-dimensional airfoil model of the present invention includes: a pressure sensor group, a plurality of first conduits 8, a second conduit 9 and a cavity 5. Each pressure sensor 7 of the pressure sensor group is vertically fixed in a mounting hole on the surface of the two-dimensional airfoil model, and the pressure measuring surface of each pressure sensor 7 in the pressure sensor group is vertical to the surface of the two-dimensional airfoil model; and the surface of the two-dimensional airfoil model is provided with a plurality of mounting holes vertical to the surface of the two-dimensional airfoil model.
The cavity 5 is fixed inside the two-dimensional airfoil model; the reference pressure end of the pressure sensor in the pressure sensor group is connected to the cavity through the first conduit 8, and a plurality of pressure sensors in the pressure sensor group correspond to the first conduits 8 one by one; the cavity 5 is connected to a first end of the second duct 9, and a second end of the second duct 9 is disposed in the atmosphere outside the two-dimensional airfoil model.
The two-dimensional airfoil model consists of a first end section 1, a middle section 2 and a second end section 3, the two-dimensional airfoil model is fixed in pairs by pins to ensure that relative rotation does not occur in an experiment, and the first end section 1, the middle section 2 and the second end section 3 are fixed in a spreading direction in a gluing mode to ensure the integrity of the upper surface and the lower surface. Wherein first end section 1 is the same with second end section 3, and inside digs a plurality of through-holes along the spanwise for whole two-dimensional airfoil model includes a plurality of through-holes in the spanwise, pivot 11 is arranged in the second through-hole of two-dimensional airfoil model geometry leading edge side, and the purpose of remaining a plurality of through-holes is in the quality of lightening the model under the condition of guaranteeing model intensity, in order to reduce its inertia. In a specific embodiment, the number of the through holes is determined according to actual requirements, for example, if the NACA0018 airfoil is adopted as a two-dimensional airfoil model, 8 through holes may be formed at this time.
The pressure sensor 7, the first conduit 8 and the cavity 5 are fixed inside the intermediate section 2, and the purpose of the first end section 1 and the second end section 3 is to ensure the integrity of the model, so that the sensor data at the positions on both sides of the intermediate section 2 are not affected by other factors. The pressure sensor group comprises a first sensor group and a second sensor group, and the first sensor group and the second sensor group respectively comprise a plurality of pressure sensors; the first sensor group is fixed in the mounting hole in the upper surface of the two-dimensional airfoil model, the second sensor group is fixed in the mounting hole in the lower surface of the two-dimensional airfoil model, and the number of the pressure sensors of the first sensor group is larger than that of the second sensor group. As shown in fig. 1-4, the first sensor group in the figure comprises 14 pressure sensors, i.e. 14 pressure sensors are installed on the upper surface (front surface) of the two-dimensional airfoil model; the second sensor group comprises 8 pressure sensors, namely 8 pressure sensors are arranged on the lower surface (the reverse surface) of the two-dimensional airfoil model.
Because the pressure sensors at the geometric rear edge are installed too tightly, the upper surface and the lower surface of the model can be mutually influenced when being installed, therefore, the chordwise positions of the pressure sensors are kept unchanged, and the spanwise positions of the pressure sensors are changed, so that the pressure sensors on the upper surface and the lower surface of the model are mutually staggered. As shown in FIG. 5, the pressure sensors of the first sensor group and the pressure sensors of the second sensor group are staggered in the chordwise direction of the two-dimensional airfoil model. Because the two-dimensional airfoil model is perpendicular to the incoming flow during the experiment, the pressure data on the same airfoil can still be obtained by adopting the installation mode. In the test, because the normal force coefficient, the axial force coefficient, the lift coefficient, the drag coefficient and the 1/4 chord line moment coefficient of the airfoil are obtained through pressure data measured by the pressure sensor 7, the pressure sensors 7 are installed on the whole airfoil, wherein 14 airfoil models are installed on the upper surface, and 8 airfoil models are installed on the lower surface. Because the sensing mechanism of the invention is mainly applied to the dynamic stall experimental study of the rotor reverse flow area, more accurate data at the geometrical trailing edge is required to be obtained, and the pressure sensor 7 at the geometrical trailing edge is more tightly installed.
The cavity 5 of the invention is placed inside the front face of the intermediate section 2, as shown in fig. 6, the reference pressure of all the pressure sensors 7 being unified to the cavity 5 by means of a first conduit 8 and then connected to the atmosphere by means of a second conduit 9. After the pressure sensor 7 and the cavity 5 are installed, the front cover plate 4 and the back cover plate 13 cover the middle section 2 of the two-dimensional airfoil model so as to ensure the integrity of the surface of the airfoil model.
Due to the special structure of the pressure sensor 7, the upper surface of the pressure sensor has a vent hole in the middle and the periphery of the pressure sensor also has a vent hole, so that a certain gap between the gasket 12 and the upper surface of the pressure sensor 7 must be ensured, and therefore, the mounting hole of the two-dimensional airfoil model surface of the invention is a two-stage stepped hole, as shown in fig. 7, the stepped hole comprises a first hole section and a second hole section, the first hole section is a hole section close to the inner part of the two-dimensional airfoil model, the second hole section is a hole section close to the surface of the two-dimensional airfoil model, and the diameter of the first hole section is smaller than that of the second hole section. The pressure sensor 7 and the two-dimensional airfoil model middle section 2 are installed by digging a groove in the model, drilling a stepped hole from the outer surface of the model to the inner side by a vertical surface, and installing the pressure sensor 7 from the inside so as to ensure the integrity of the surface of the model. A step through hole is drilled in the two-dimensional airfoil model middle section 2 from outside to inside in the direction perpendicular to the surface of the model according to the installation position of the sensor, and a groove is dug at the corresponding position in the model, so that the arrangement of the first conduit 8 and the signal line 10 is facilitated. Specifically, a first groove and a second groove are formed in the middle section 2. The cavity 5 is fixed in the first groove, part of the pipe section of the first end of the second pipe 9 is positioned in the first groove, and part of the pipe section of the second end of the second pipe 9 passes through the through hole in the first end section and extends to the outside of the two-dimensional airfoil model. The second groove is in communication with the first groove. A plurality of said first conduits 8 are fixed in said second recess, a first end of the first conduit 8 being connected to a reference pressure end of a pressure sensor 7 of the pressure sensor group, and a second end of the second conduit 8 being connected to said cavity 5 in the first recess. And the signal wires of the pressure sensor group are converged into the first groove through the second groove and finally pass through the through hole in the second end section 3 to extend to the outside of the two-dimensional airfoil model.
In order to ensure the integrity of the surface of the model, the stepped through holes on the model need to be filled with gaskets 12, the surface of the model is a curved surface, the gaskets 12 are a plane, and the stepped through holes need to be polished after the installation so as to keep the smoothness of the surface of the model. Since the pressure sensor 7 is a high-precision element, in order to prevent debris from entering the pressure sensor 7 during the polishing process, it must be ensured that the gasket 12 is installed first and then the pressure sensor 7 is installed in the order of installing the pressure sensor 7 and the gasket 12. The pressure sensors on the back surface and the front surface of the two-dimensional airfoil model are mounted by the same mounting method, and the only difference is that the cavity 5 is not required to be placed in the groove on the back surface, but is directly connected with the cavity 5 in the groove on the front surface through the 8 first guide pipes.
With respect to the parameters of the respective devices in the present invention, the present invention gives the following examples:
the two-dimensional airfoil model adopts an NACA0018 airfoil with the specification of 1000X 300. The ABS plastic is used as the model material, and has higher strength and rigidity and smaller mass compared with other materials. The purposes of selecting the wing profile mainly include two purposes: one is that the airfoil has small curvature and large thickness, the pressure sensor can be installed at the geometric trailing edge as far as possible, and can be arranged more densely, so that more data can be measured, and the later experimental data is closer to the real situation during interpolation; secondly, the wing profile is thicker, and more available space is arranged in the wing profile for arranging signal wires of the sensor. 22 holes perpendicular to the surface of the model are dug at proper positions on the surface of the blade model so as to be convenient for installing the miniature dynamic pressure sensor and ensure that the pressure measuring surface is perpendicular to the surface of the model. And grooves are dug in the blade model, so that a first conduit and a signal wire of the miniature dynamic pressure sensor can be conveniently arranged.
The pressure sensor 7 adopts an HTP504 miniature dynamic pressure sensor with the frequency of 3KHz, and has the advantages of small volume, light weight, 0-2 Kpa of measuring range and less than two thousandths of error range. The pressure measurement device can be arranged in the model in a mode of being perpendicular to the surface of the airfoil, and can be used for static pressure measurement and dynamic pressure measurement.
The cavity 5 is a cuboid cavity with the specification of 70X40X10, the wall thickness of the cavity is 2mm, and the cavity is made of common transparent ABS. The left side of the cavity needs to be drilled with 8 holes with the diameter of 2.2mm, the right side needs to be drilled with 14 holes with the diameter of 2.2mm, and a cavity connecting pipe 6 is inserted for connecting a first conduit 8 of a reference pressure end of a pressure sensor 7. The first guide duct 8 is an aluminum pipe having a length of 10mm, an outer diameter of 2.2mm and an inner diameter of 1 mm.
The second conduit 9 is a flexible rubber hose with an inner diameter of 2.2 mm.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (9)
1. A sensing mechanism for a two-dimensional airfoil model, comprising: a pressure sensor group, a plurality of first conduits, a second conduit, and a cavity;
the pressure sensor group is vertically fixed in a mounting hole on the surface of the two-dimensional airfoil model, and the pressure measuring surface of each pressure sensor in the pressure sensor group is vertical to the surface of the two-dimensional airfoil model; the surface of the two-dimensional airfoil model is provided with a plurality of mounting holes perpendicular to the surface of the two-dimensional airfoil model; the pressure sensor group comprises a first sensor group and a second sensor group, and the first sensor group and the second sensor group both comprise a plurality of pressure sensors; the first sensor group is fixed in a mounting hole in the upper surface of the two-dimensional airfoil model, and the second sensor group is fixed in a mounting hole in the lower surface of the two-dimensional airfoil model; the pressure sensors of the first sensor group and the pressure sensors of the second sensor group are arranged in a staggered mode in the chord direction of the two-dimensional airfoil model;
the cavity is fixed inside the two-dimensional airfoil model; the reference pressure end of the pressure sensor in the pressure sensor group is connected to the cavity through the first guide pipe, and a plurality of pressure sensors in the pressure sensor group correspond to the first guide pipes one by one; the cavity is connected to a first end of the second conduit, and a second end of the second conduit is disposed in the atmosphere outside the two-dimensional airfoil model.
2. The sensing mechanism of a two-dimensional airfoil model according to claim 1, wherein the two-dimensional airfoil model is provided with a plurality of through holes along the span direction, and the rotating shaft of the two-dimensional airfoil model is placed in the second through hole on the geometric leading edge side of the two-dimensional airfoil model.
3. The sensing mechanism of the two-dimensional airfoil model according to claim 2, wherein the two-dimensional airfoil model comprises a first end section, a middle section and a second end section, the first end section, the middle section and the second end section are sequentially fixed by pins, and the first end section, the middle section and the second end section are fixed in a spanwise direction in a gluing mode; the pressure sensor set, the first conduit, and the cavity are all located within the intermediate section.
4. The sensing mechanism of the two-dimensional airfoil model as claimed in claim 3, wherein the middle section is internally provided with a first groove and a second groove;
the cavity is fixed in the first groove, part of the pipe section of the first end of the second pipe is positioned in the first groove, and part of the pipe section of the second end of the second pipe passes through the through hole in the first end section and extends to the outside of the two-dimensional airfoil model;
a plurality of said first conduits being secured within said second recess;
the second groove is communicated with the first groove; and a signal wire of the pressure sensor group sequentially passes through the second groove, the first groove and the through hole in the second end section to extend to the outside of the two-dimensional airfoil model.
5. The sensing mechanism of a two-dimensional airfoil model according to claim 1, characterized in that the number of pressure sensors of said first sensor group is greater than the number of pressure sensors of said second sensor group.
6. The sensing mechanism of a two-dimensional airfoil model according to claim 5, characterized in that said first sensor group comprises 14 pressure sensors and said second sensor group comprises 8 pressure sensors.
7. The sensing mechanism of the two-dimensional airfoil model according to claim 1, characterized in that the pressure sensors in the pressure sensor group are HTP504 type micro dynamic pressure sensors.
8. The sensing mechanism of a two-dimensional airfoil model according to claim 7, wherein the mounting hole of the two-dimensional airfoil model surface is a stepped hole, the stepped hole comprises a first hole section and a second hole section, the first hole section is a hole section near the two-dimensional airfoil model inner hole section, the second hole section is a hole section near the two-dimensional airfoil model surface, and the diameter of the first hole section is smaller than the diameter of the second hole section.
9. The sensing mechanism for a two-dimensional airfoil model as recited in claim 8, wherein said mounting hole further comprises a spacer at a second hole end of said second hole segment, said spacer for filling a portion of said two-dimensional airfoil model surface that is free at said mounting hole location; and the second hole end of the second hole section is one end positioned on the surface of the two-dimensional airfoil model, and the first hole end of the second hole section is connected with the first hole section.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010473766.7A CN111579204B (en) | 2020-05-29 | 2020-05-29 | Sensing mechanism of two-dimensional airfoil model |
| AU2020102021A AU2020102021A4 (en) | 2020-05-29 | 2020-08-27 | Sensing Mechanism of Two-Dimensional Airfoil Model |
| US17/333,119 US11131599B1 (en) | 2020-05-29 | 2021-05-28 | Sensing mechanism of two-dimensional airfoil model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010473766.7A CN111579204B (en) | 2020-05-29 | 2020-05-29 | Sensing mechanism of two-dimensional airfoil model |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111579204A CN111579204A (en) | 2020-08-25 |
| CN111579204B true CN111579204B (en) | 2021-03-16 |
Family
ID=72119712
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010473766.7A Active CN111579204B (en) | 2020-05-29 | 2020-05-29 | Sensing mechanism of two-dimensional airfoil model |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US11131599B1 (en) |
| CN (1) | CN111579204B (en) |
| AU (1) | AU2020102021A4 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114354147B (en) * | 2021-10-22 | 2023-06-20 | 中国华能集团清洁能源技术研究院有限公司 | Wind generating set blade environment damage test system and method and application thereof |
| CN113942642B (en) * | 2021-11-19 | 2023-09-08 | 中国直升机设计研究所 | Helicopter blade with pneumatic pressure measurement sensor |
| CN114942119B (en) * | 2022-04-21 | 2023-10-03 | 北京理工大学 | High-temperature high-speed rotating impeller machinery transient flow field test system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014123938A1 (en) * | 2013-02-05 | 2014-08-14 | International Electronic Machines Corporation | Pressure profiling system |
| CN104807609A (en) * | 2015-05-04 | 2015-07-29 | 中国科学院工程热物理研究所 | Pneumatic wind blade pressure testing structure |
| CN104943195A (en) * | 2015-05-04 | 2015-09-30 | 中国科学院工程热物理研究所 | Embedding method for pneumatic piezometer tube of wind-power blade based on vacuum suction pouring forming |
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile sideway oscillation flow tunnel testing device |
| CN109808913A (en) * | 2019-01-29 | 2019-05-28 | 西北工业大学 | A kind of unmanned aerial vehicle design method with deflectable winglet |
| CN110500240A (en) * | 2019-09-27 | 2019-11-26 | 扬州大学 | The measurement method of small-power wind energy conversion system aerodynamic characteristic |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4770032A (en) * | 1987-02-05 | 1988-09-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Porous plug for reducing orifice induced pressure error in airfoils |
| US5513526A (en) * | 1994-07-20 | 1996-05-07 | The United States Of America As Represented By The Secretary Of The Navy | Hydrofoil force balance |
| JP4446608B2 (en) * | 2001-01-09 | 2010-04-07 | 本田技研工業株式会社 | Wind tunnel test model |
| WO2010006033A1 (en) * | 2008-07-08 | 2010-01-14 | Tao Of Systems Integration, Inc. | Method for predicting flow and performance characteristics of a body using critical point location |
| US7845236B2 (en) * | 2008-08-26 | 2010-12-07 | General Electric Company | Resistive contact sensors for large blade and airfoil pressure and flow separation measurements |
| CN104978449A (en) * | 2015-08-17 | 2015-10-14 | 北京航空航天大学 | Aerodynamic optimization method of leading edge slats position and trailing edge flap position of two-dimensional three-section airfoil profile |
-
2020
- 2020-05-29 CN CN202010473766.7A patent/CN111579204B/en active Active
- 2020-08-27 AU AU2020102021A patent/AU2020102021A4/en not_active Ceased
-
2021
- 2021-05-28 US US17/333,119 patent/US11131599B1/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014123938A1 (en) * | 2013-02-05 | 2014-08-14 | International Electronic Machines Corporation | Pressure profiling system |
| CN104807609A (en) * | 2015-05-04 | 2015-07-29 | 中国科学院工程热物理研究所 | Pneumatic wind blade pressure testing structure |
| CN104943195A (en) * | 2015-05-04 | 2015-09-30 | 中国科学院工程热物理研究所 | Embedding method for pneumatic piezometer tube of wind-power blade based on vacuum suction pouring forming |
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile sideway oscillation flow tunnel testing device |
| CN109808913A (en) * | 2019-01-29 | 2019-05-28 | 西北工业大学 | A kind of unmanned aerial vehicle design method with deflectable winglet |
| CN110500240A (en) * | 2019-09-27 | 2019-11-26 | 扬州大学 | The measurement method of small-power wind energy conversion system aerodynamic characteristic |
Non-Patent Citations (2)
| Title |
|---|
| Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model;YeYuan;《Aerospace Science and Technology》;20181103;第293-304页 * |
| 风力机叶片翼型动态试验技术研究;李国强;《力学学报》;20180430;第50卷(第4期);第751-765页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111579204A (en) | 2020-08-25 |
| AU2020102021A4 (en) | 2020-10-01 |
| US11131599B1 (en) | 2021-09-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111579204B (en) | Sensing mechanism of two-dimensional airfoil model | |
| Moreau et al. | Effect of airfoil aerodynamic loading on trailing edge noise sources | |
| CN103443454A (en) | Wind turbine blade with air pressure sensors | |
| Nakayama | Characteristics of the flow around conventional and supercritical airfoils | |
| US20050188759A1 (en) | Pressure distribution measuring system | |
| CN110849575A (en) | Wind turbine complete machine aerodynamic force measuring system and method | |
| CN108692912A (en) | A kind of double frictional resistance balance measurement methods of swimming cloths | |
| CN115266001A (en) | Two-degree-of-freedom pneumatic elasticity experimental device | |
| Jiang et al. | Control of rotor trailing edge noise using porous additively manufactured blades | |
| CN103018002B (en) | Testing device and method for measuring wind drag of automobile model | |
| CN116499703A (en) | Quantitative analysis method suitable for friction-reducing resistance effect under external flow condition | |
| CN111537186B (en) | Helicopter rotor blade model with embedded pressure sensor and manufacturing process thereof | |
| Lakshminarayana | An axial flow research compressor facility designed for flow measurement in rotor passages | |
| CN112729752B (en) | Spaceflight friction resistance sensor based on K-shaped pipe differential pressure measurement | |
| CN216209247U (en) | Vane type sensor for measuring pneumatic data | |
| CN112894281B (en) | Method for machining aerospace friction resistance sensor gauge head structure based on multiple machining datum planes | |
| Bicknell | Determination of the profile drag of an airplane wing in flight at high Reynolds numbers | |
| Sitorus et al. | Hydrodynamic characteristics of cambered NACA0012 for flexible-wing application of a flapping-type tidal stream energy harvesting system | |
| CN111579203A (en) | Two-dimensional airfoil pressure measurement system | |
| Roepke | An experimental investigation of a Goldschmied propulsor | |
| Miller | High Reynolds number horizontal and vertical axis wind turbine experiments | |
| Reich et al. | Full-Scale Reynolds Number Testing of Rotor Hub Drag and Wake Turbulence | |
| CN217111402U (en) | Elastic wing pulsating pressure test model | |
| CN109625316A (en) | The measurement method of hinge moment on the inside of super high aspect ratio wing rudder face | |
| CN106840594A (en) | A kind of four hole dynamic pressure probes for measuring transonic speed three-dimensional non-steady flow field |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |